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Gas Turbine Blade Failure Analysis by Yemane Tesfaye is a document available to read on EtoBox.
The document summarizes a study analyzing heat transfer, stress, and failure in a gas turbine blade with internal circular cooling passages. 3D numerical simulations were performed using commercial codes CFX and ANSYS to calculate heat transfer coefficients and stresses. The highest heat transfer coefficient occurred at the leading edge stagnation point due to impingement. The lowest occurred at the trailing edge due to thermal boundary layer development. However, the maximum temperature and thermal stress
- Author
- Yemane Tesfaye
- Language
- EN